From Summary: "A review of the status of the knowledge on turbine-blade cooling and a description of pertinent NACA investigations are presented. The current limitations in performance of uncooled and cooled engines are briefly discussed. Finally, the knowledge available and investigations to increase the knowledge on heat transfer, cooling-flow, and performance characteristics of cooled turbines are discussed."

"Free-flight tests have been made to determine the drag at zero lift of several configurations of a missile having triangular wings and tails. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8" (p. 1).

The following report describes a chemical procedure to analyze fission products and long-lived rare earths in both untreated urine samples and the supernates from the precipitation steps in the TTA procedure for plutonium.

Report discussing a performance evaluation of the Thermal Test Unit, a piece of test equipment fabricated to "aid the Hanford Works in experimentally determining heat transfer characteristics for a particular application."

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks" (p. 1).

"The particular integrals of the second-order and third-order Prandtl-Busemann iteration equations for the flow of a compressible fluid are obtained by means of the method in which the complex conjugate variables are utilized as the independent variables of the analysis. The assumption is made that the Prandtl-Glauert solution of the linearized or first-order iteration equation for the two-dimensional flow of a compressible fluid is known. The forms of the particular integrals, derived for subsonic flow, are readily adapted to supersonic flows with only a change in sign of one of the parameters of the problem" (p. 909).

Report discussing study on recovery of nitric acid in the uranium recovery process. The behavior of chloride ions and tributyl phophate is noted, and the quality of recycled nitric acid was tested. Stainless steel in the nitric acid recovery system was evaluated for corrosion.

Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.

"Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).

Report presenting data gathered on a lateral-trim change or wing dropping that involves a rapid change of lateral trim with Mach number, which has occurred on several rocket-powered models used in roll investigations at transonic speeds. The data in this report demonstrates that straight wings with airfoil sections 9 percent thick or greater are susceptible to wing dropping between Mach numbers of 0.9 and 1.0. Results for straight, sweptback, and delta wings are provided.

A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.

Report presenting a method for calculating the lift distribution due to twist which gives a closer approximation than the current Schrenk empirical method and requires about the same amount of computing. The method uses the lifting-line theory and makes use of the lift distribution due to angle of attack and considers the aspect ratio of the wing. Examples are presented for four main types of twist: symmetrical, antisymmetrical, continuous, and discontinuous.

Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.

"The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).

"A general integral form of the boundary-layer equation, valid for either laminar or turbulent incompressible boundary-layer flow, is derived. By using the experimental finding that all velocity profiles of the turbulent boundary layer form essentially a single-parameter family, the general equation is changed to an equation for the space rate of change of the velocity-profile shape parameter. The lack of precise knowledge concerning the surface shear and the distribution of the shearing stress across turbulent boundary layers prevented the attainment of a reliable method for calculating the behavior of turbulent boundary layers" (p. 1067).

From Summary: "An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations."

The stage performance of the X24C-2 axial-flow compressor, as determined from radial distributions of total pressure and temperature measured in each stator-blade row, was investigated at design speed at weight flows corresponding to those of the maximum weight-flow, peak-efficiency, and surge points. The stage performance is presented as the measured stage pressure ratios and the calculated velocity diagrams. The average stage total-pressure ratio at the surge operating condition in the first stage was approximately 1.10; in the second stage, approximately 1.13; and in all remaining stages, approximately constant at a value of 1.15. Regions of inefficient flow are discussed so as to point out the reasons for the poor flow conditions.

Part I of this report covers critical-mass determinations for pseudospheres of oralloy hydride composition (approximating UH3) in 8"-thick Tu and Ni tampers and in the Tu tamper with Ni liner. The critical mass of a hydride cube in the thick Tu also is given. Data on weight and dimensional changes of hydride pieces during the period of use are included. In Part II are presented the results of Rossi time-scale measurements on the hydride assemblies. Values of alpha at delayed critical and its variation with mass in the neighborhood of delayed critical are given. Measurements on the activation of various detectors within the hydride assemblies are described in Part III. Results as a function of radial position are given for Au, for Au shielded by Au and by Cd, for S and for fission catchers with U235 and U238. Reactivity changes resulting from the introduction of foreign materials into the hydride assemblies are discussed in Part IV. Apparent regularities with respect to Z and qualitative interpretations of variations with radius are pointed out. From data for various radial positions, changes in critical mass corresponding to small changes in composition and density are computed.

Report presenting flight measurements in sideslips of the static lateral and directional stability characteristics of the Douglas D-558-II airplane. It is part of an investigation to determine the stability and control characteristics and aerodynamic loads acting on the wing and horizontal tail of an airplane from stalling speed up to a maximum Mach number of 0.90. Results regarding variations of rudder, total aileron, elevator control positions and control forces, aileron position, and aerodynamic hinge moments are provided.

Report presenting the aerodynamic properties of a model of a jettisonable nose section with a circular cross section as determined at low speed from an investigation in the 20-foot free-spinning tunnel. The results indicated that the aerodynamic characteristics of the nose were greatly affected by proximity to the fuselage. Even for a stabilized nose, it may be necessary to eject the nose forward forcibly in order to prevent high accelerations along the backbone of the pilot.

Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."

The fifth report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(0)(066)-03 propeller.

Report summarizing physical studies on Redox solutions and metal waste solutions, including refractometric investigations.

The following report provides results from laboratory tests on the corrosion resistance of various types of stellite facings on astenitic stainless steel T-347 to Redox streams.